grace-fo laser ranging instrument: german contributiongrace (gravity recovery and climate...

GRACE-FOLaser Ranging Instrument:

German contribution

J. Sanjuan on behalf of the LRI team

Deutsches Zentrum fur Luft- und Raumfahrt (DLR)

Gainesville, FL, May 22, 2014

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GRACE (Gravity Recovery And Climate Experiment)

I Joint US/German mission (launched March 2002)I Maps the Earth’s gravity field variations (glacials,

deformation, hydrology, etc.)I 2 SC separated by 220 km in a near polar orbit

(500 km)I Two-way microwave-ranging linkI End of mission: expected 2015-2016

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GRACE (Gravity Recovery And Climate Experiment)

I Joint US/German mission (launched March 2002)I Maps the Earth’s gravity field variations (glacials,

deformation, hydrology, etc.)I 2 SC separated by 220 km in a near polar orbit

(500 km)I Two-way microwave-ranging linkI End of mission: expected 2015-2016

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GRACE (Gravity Recovery And Climate Experiment)

I Joint US/German mission (launched March 2002)I Maps the Earth’s gravity field variations (glacials,

deformation, hydrology, etc.)I 2 SC separated by 220 km in a near polar orbit

(500 km)I Two-way microwave-ranging linkI End of mission: expected 2015-2016

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GRACE-Follow On

I To minimize data gap between GRACE and nextgeneration gravity field missions: near rebuild ofGRACE

I Launch: August 2017I Add-on: Laser Ranging Instrument (LRI) as a

technology demonstratorI First inter-satellite laser interferometer

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Race-track configuration

I Heterodyne interferometry: 4 MHz-16 MHzI “Slave” SC offset phase locked (active transponder)

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LRI subsystems and team roles

I Germany (AEI/GFZ/STI/DLR/Astrium)I Triple mirror assembly (TMA)I Optical bench assembly (OBA)

I US (JPL/Ball Aerospace/Tesat GmbH)I Frequency stabilization systemI Phasemeter and payload processing electronicsI Laser source

I Australia (ANU/EOS/CSIRO)I Triple mirror prototypingI Acquisition experiments

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TMA: large-lateral offset retroreflector

I 3 orthogonal mirrorsI 2p=600 mmI Routes the beam around

cold gas tank and MWRI Places the vertex at the

accelerometerI Rotation (SC jitter) around

virtual vertex maintains:I Round-trip pathlengthI Anti-parallel beams

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TMAI Requirements

δx(f ) . 50× NSF(f ) nm Hz−1/2

kroll . 10µm rad−1

kpitch,yaw . 100µmrad−1

I TMA vertex/accelerometer must be within ∼100µm

x∆ y∆ z∆

θx

θz

θy

x∆

y∆z∆

y∆

x∆ θy

x∆ θz

0 0 0

0

0x

y

−

I Roll jitter (θx) also couples for a non-ideal TMA:coalignment .40µrad

I Thermal effects7 / 17

QM TMA

I TMA design by STII DM and QM tested for performance and environment

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Optical bench assembly (OBA)I Measures the phase difference between the LO and

the far SC beamI Measures the relative angle between the LO and the

far SC beam (DWS)I Steers the local beam to align it with the far SC beam

I SC pointing not sufficient to keep lockI Control loop zeros DWS to keep beams aligned

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Pointing control

I Ideal position

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Pointing control

I SC rotates

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Pointing control

I DWS-steering mirror correction

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OBA components

I Quadrant photoreceiverI Type: InGaAsI Bandwidth: 4 MHz-16 MHzI Noise: 5 pA Hz−1/2

I Size: 1 mm diameterI Fast steering mirror

I Voice coil motors and position measurement (Kaman)I Dynamic range: ±8.1 mradI ±3 mrad at 150 Hz ('2 rad s−1)

I Fiber injector assemblyI Quartz block-aspheric lensI Beam radius: 2.5 mmI Collimated beam planarity ≤ λ/15

I Imaging opticsI Compensation plate

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OBA components

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OBA

Fiber injector assembly Photoreceiver front−end

Fast steering mirror

Position sensor system

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Acquisition strategyI 5 DoF (2 angles on each SC plus laser frequency)I No real time communication between SCI Needed:

I Small beam divergence angle (±200µrad)I Small frequency range (12 MHz)

I Starting point:I Large initial pointing uncertainty (±3 mrad)I Large initial frequency offset uncertainty (400 MHz)

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Acquisition procedure

I Scan over the complete uncertainty space: 9 hoursI Send data to groundI Search for the maximum detector outputI Estimate the line of sight and frequency

I Only once the unknown pointing biases needs to bedetermined, which are caused by integrationtolerances, launch vibrations, g-release, etc.

I Update information to SCI Re-acquisition algorithm (reduced parameter space):<1 minute

I Enable DWS

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Acquisition procedure

0.56 s

11 min

7 MHz

6 mrad

6 m

rad

6 m

rad

6 mrad

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Summary

I GRACE-FO will be the first inter-satellite laserinterferometer

I Expected to generate better data than MWRI Expected to provide valuable information for LISAI German subsystems at CDR level:

I TMA: CDR passed on March 2014 (FMs will be readyby the end of 2014)

I OBA: CDR currently taking place (May 2014)I Exhaustive analysis, simulations and experiments

have validated the acquisition algorithms

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